US3912418A - Lubrication system for a rotor - Google Patents

Lubrication system for a rotor Download PDF

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Publication number
US3912418A
US3912418A US510932A US51093274A US3912418A US 3912418 A US3912418 A US 3912418A US 510932 A US510932 A US 510932A US 51093274 A US51093274 A US 51093274A US 3912418 A US3912418 A US 3912418A
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US
United States
Prior art keywords
oil
rotor
housing
chamber
drive shaft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US510932A
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English (en)
Inventor
Merritt B Andrews
Philip E Barnes
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to US510932A priority Critical patent/US3912418A/en
Priority to JP50117609A priority patent/JPS5162259A/ja
Priority to GB40095/75A priority patent/GB1516349A/en
Priority to FR7530010A priority patent/FR2286949A1/fr
Application granted granted Critical
Publication of US3912418A publication Critical patent/US3912418A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms

Definitions

  • This invention relates to a lubrication system for the fan of a ducted fan propulsor.
  • a conventional method of lubricating a fan or propeller is by completely filling the hub or housing carrying the rotating assemblies. Such a system would require constant checking to assure that the oil was at the proper level. Also, by completely filling, the system virtually carries an excess of oil that adds to the weight of the assembly, which, particularly for aircraft applica- -tions is undesirable.
  • the rotor is not rotating the oil that was held centrifugally will drop to the bottom half to the drain point level, which preferably is adjacent to the rotor drive shaft.
  • the object of this invention is to provide an improved lubrication system for a rotor.
  • the important feature of this invention is to provide, particularly for a variable pitch fan or the like that includes a rotor housing different rotating assemblies, means for continuously feeding an oil replenishing chamber and draining off the excess oil during rotation, damming the flooded areas to form an oil ring, and interconnecting the dammed areas and replenishing chamber, so that oil drops gravitationally during rotor stoppage, so that the oil from the replenishing chamber replenishes oil in the dammed area for the next rotative cycle.
  • FIG. 1 is a view schematically illustrating a ducted fan propulsor.
  • FIG. 2 is a schematic representation of the principles of this invention showing the nonrotation condition.
  • FIG. 3 is a schematic representation of the principles of this invention showing the rotating condition.
  • FIG. 4 is a view partly in elevation, partly in section and partly in schematic illustrating a practical application of this invention.
  • a Q-Fan propulsor is a variable pitch ducted fan as shown in FIG. 1 comprising the fan rotor generally illustrated by numeral supporting a plurality of variable pitch fan blades 14 within the engine bypass duct 16 supported to the turbine power plant 18 by anti-swirl vanes 20.
  • the lubrication system serves to provide oil in selected areas within the rotor radially spaced from the drive shaft by flooding these areas where parts intended to be lubricated are located and forming a dam accessible from the shaft.
  • a replenishing chamber 22 is constantly fed oil while the rotor is in the rotating condition as schematically shown by dash lines 24. Any excess oil beyond this level will be carried back to drain which is always in communication as illustrated by dash line 24 leaving through the rearward end of the rotor.
  • the hub 30 driven by the engine drive shaft 32 which supports the blades 34.
  • the dammed area 28 obviously, lubricates the bearings supporting blades 34 for pitch change movement.
  • the dammed area 26 lubricates the pitch change actuating mechanism and the replenishing chamber 22 serves to replenish the oil losses, as will be explained hereinbelow and the flow to and out of the chamber is utilized to lubricate the bearings supporting the hub to the shaft, the drive gearing, bearings and the like.
  • the centrifugal field in the hub serves to hold the oil in the dammed areas so that a centrifugal ring of oil is formed around these parts.
  • the input to the harmonic drive is through actuator 56 (shown in blank and schematically) which rotates gear 58.
  • the input, through the customary type of differential gearing 60 drives wave generator 62 causing relative motion between rigid spline 64 and flexible spline 66 grounded to hub 40 at the spline connector 68.
  • pitch change is effectuated in response to the input by rotating spline 64 which in turn rotates the blade 42 via gears 50 and 52. It is also apparent that the parts are so arranged to form pockets interconnected to each other by virtue of the cavity portion of the hub.
  • oil which is introduced through the spray nozzle 70 shown schematically at the differential flows through annular passage 72 through aperture 74 to fill cavity 76, lubricating the area where bearings 78, 80, 82 and 84 are located.
  • the bearings are not flooded with oil and the oil leaking from cavity 76 must pass through a restrictive flow path before reaching the drain sump.
  • suitable seals like labyrinth seal 86 are incorporated in all locations where oil may escape unwantedly.
  • a drain line located at the rear end of the rotor provides continuous leakage path for excessive oil and is shown schematically by arrow 88 returning oil to the sump schematically shown by tank 90.
  • Any suitable pump 92 may be employed.
  • the area just described represents the replenishing pocket and what is shown schematicaly in FIG. 3 as chamber 22. Here oil is continuously being introduced when the rotor is in the rotary condition.
  • a second pocket, corresponding to chamber 26 of PK]. 3 is adjacent the harmonic drive and is defined by the housing wall 94 and the annular depending member 96. And the other pocket is defined by the hub wall and blade root, it being noted that there is communication between each of these pockets so that oil can freely migrate thereto when the rotor is not rotating.
  • a lubrication system for a rotor having a housing supporting variable pitch blades including a drive shaft driving said rotor, a pitch change actuator including elements having relative movement, support means for the blades including elements having relative movement and the drive shaft including elements having relative movement, all of said elements requiring lubrication and being disposed in said housing such that said support means, said pitch change actuator and said drive shaft are radially spaced from each other defining separate lubrication areas and all being supported in the cavity of said housing so that there is intercommunication between all of said areas so that oil can migrate from adjacent one set of elements to another set of elements when the rotor is in a nonrotating condition, a chamber in said housing for receiving oil when said rotor is rotating, drain means communicating with said chamber to exit the excess oil from said chamber and establish a relative level of oil in said cavity when said rotor is nonrotating, and oil supply means for continuously feeding oil to said chamber solely when said rotor is rotating, whereby when said rotor stops rotating the oil will gravitate to the bottom of
  • a lubricating system as claimed in claim 1 including pump means for pumping oil from said supply means.
  • a lubrication system for a rotor having a housing supporting a plurality of blades, pitch change actuation means in said housing and driving means in said housing for rotating said rotor, said housing being generally annular in shape having the drive shaft connected centrally thereof, the blades supported at the outer periphery thereof, and the pitch change actuator disposed therebetween, wall means extending in and including said housing defining given dammed areas such that the portion supporting said blades, and the pitch change actuation means each defining a spaced annular portion where lubrication is required and where a centrifugal ring of oil is formed therein when the rotor is rotating and there being intercommunication with each dammed area so that when the rotor is nonrotating the oil in the top half of the annular housing will drop to the lower half flooding said dammed areas, drain means located substantially centrally of said housing establishing a predetermined level of oil, a replenishing chamber substantially annular in shape adjacent said driving means for continuously receiving oil when the rotor rotates and where oil is held centri

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Details Of Gearings (AREA)
US510932A 1974-10-01 1974-10-01 Lubrication system for a rotor Expired - Lifetime US3912418A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US510932A US3912418A (en) 1974-10-01 1974-10-01 Lubrication system for a rotor
JP50117609A JPS5162259A (en) 1974-10-01 1975-09-29 Rootanotameno junkatsukei
GB40095/75A GB1516349A (en) 1974-10-01 1975-10-01 Lubrication system for a bladed rotor
FR7530010A FR2286949A1 (fr) 1974-10-01 1975-10-01 Systeme de lubrification pour un rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US510932A US3912418A (en) 1974-10-01 1974-10-01 Lubrication system for a rotor

Publications (1)

Publication Number Publication Date
US3912418A true US3912418A (en) 1975-10-14

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ID=24032784

Family Applications (1)

Application Number Title Priority Date Filing Date
US510932A Expired - Lifetime US3912418A (en) 1974-10-01 1974-10-01 Lubrication system for a rotor

Country Status (4)

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US (1) US3912418A (enExample)
JP (1) JPS5162259A (enExample)
FR (1) FR2286949A1 (enExample)
GB (1) GB1516349A (enExample)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4668168A (en) * 1984-06-14 1987-05-26 J.M. Voith Gmbh Lubricating and cooling rotary bearings of axial blowers
US4693672A (en) * 1986-10-30 1987-09-15 United Technologies Corporation Two level oil dam
US4824327A (en) * 1987-12-15 1989-04-25 United Technologies Corporation Gas turbine engine oil drain slot
US4887424A (en) * 1987-05-06 1989-12-19 Motoren- Und Turbinen-Union Munchen Gmbh Propfan turbine engine
US5152668A (en) * 1990-07-23 1992-10-06 General Electric Company Pitch change mechanism for prop fans
US5154580A (en) * 1990-07-23 1992-10-13 General Electric Company Propeller pitch change mechanism
US5154372A (en) * 1990-07-23 1992-10-13 General Electric Company Torque multiplier for aircraft propeller
US5156648A (en) * 1990-07-09 1992-10-20 General Electric Company Prop-fan pitch-change mechanism
US5174716A (en) * 1990-07-23 1992-12-29 General Electric Company Pitch change mechanism
US5242265A (en) * 1990-07-23 1993-09-07 General Electric Company Aircraft pitch change mechanism
US6139272A (en) * 1996-04-29 2000-10-31 Kvaerner Turbin Aktiebolag Hydraulic machine
FR2964942A1 (fr) * 2010-09-22 2012-03-23 Snecma Enceinte de protection des pignons de commande du pas d'une helice d'open-rotor
US20160186584A1 (en) * 2013-08-14 2016-06-30 Snecma Turbomachine impellor rotor with device for feathering the blades of the impellor
US9677421B2 (en) 2012-10-24 2017-06-13 United Technologies Corporation Gas turbine engine rotor drain feature
US10400883B2 (en) 2017-01-04 2019-09-03 United Technologies Corporation Gear with fluid control dam and apertures
US11155334B2 (en) * 2018-03-12 2021-10-26 Ge Avio S.R.L Fan blade support assembly
US11719107B2 (en) * 2018-10-12 2023-08-08 Safran Aircraft Engines Turbine engine comprising a rotor with variable-pitch blades

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2891627A (en) * 1955-02-03 1959-06-23 Gen Motors Corp Variable pitch propeller and oil reservoir therefor
US2988154A (en) * 1956-08-10 1961-06-13 Voith Gmbh J M Blade wheel propeller
US3301330A (en) * 1964-10-16 1967-01-31 Gen Motors Corp Propeller oil level control
US3325088A (en) * 1964-03-19 1967-06-13 Rolls Royce Lubricating means for a bearing
US3339639A (en) * 1964-09-09 1967-09-05 Dowty Rotol Ltd Wind motors
US3720060A (en) * 1969-12-13 1973-03-13 Dowty Rotol Ltd Fans
US3801219A (en) * 1971-05-05 1974-04-02 Jerome A Gross Controllable pitch maripropeller
US3825370A (en) * 1971-12-11 1974-07-23 Rolls Royce 1971 Ltd Pitch varying mechanism for variable pitch fan
US3866415A (en) * 1974-02-25 1975-02-18 Gen Electric Fan blade actuator using pressurized air
US3873235A (en) * 1973-10-01 1975-03-25 Gen Electric Variable pitch turbofan engine
US3876333A (en) * 1973-02-17 1975-04-08 Dowtry Rotol Limited Gas turbine engines and bladed rotors therefor

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1386448A (fr) * 1963-12-11 1965-01-22 Rateau Soc Dispositif de graissage autonome d'organes en rotation

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2891627A (en) * 1955-02-03 1959-06-23 Gen Motors Corp Variable pitch propeller and oil reservoir therefor
US2988154A (en) * 1956-08-10 1961-06-13 Voith Gmbh J M Blade wheel propeller
US3325088A (en) * 1964-03-19 1967-06-13 Rolls Royce Lubricating means for a bearing
US3339639A (en) * 1964-09-09 1967-09-05 Dowty Rotol Ltd Wind motors
US3301330A (en) * 1964-10-16 1967-01-31 Gen Motors Corp Propeller oil level control
US3720060A (en) * 1969-12-13 1973-03-13 Dowty Rotol Ltd Fans
US3801219A (en) * 1971-05-05 1974-04-02 Jerome A Gross Controllable pitch maripropeller
US3825370A (en) * 1971-12-11 1974-07-23 Rolls Royce 1971 Ltd Pitch varying mechanism for variable pitch fan
US3876333A (en) * 1973-02-17 1975-04-08 Dowtry Rotol Limited Gas turbine engines and bladed rotors therefor
US3873235A (en) * 1973-10-01 1975-03-25 Gen Electric Variable pitch turbofan engine
US3866415A (en) * 1974-02-25 1975-02-18 Gen Electric Fan blade actuator using pressurized air

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4668168A (en) * 1984-06-14 1987-05-26 J.M. Voith Gmbh Lubricating and cooling rotary bearings of axial blowers
US4693672A (en) * 1986-10-30 1987-09-15 United Technologies Corporation Two level oil dam
US4887424A (en) * 1987-05-06 1989-12-19 Motoren- Und Turbinen-Union Munchen Gmbh Propfan turbine engine
US4824327A (en) * 1987-12-15 1989-04-25 United Technologies Corporation Gas turbine engine oil drain slot
US5156648A (en) * 1990-07-09 1992-10-20 General Electric Company Prop-fan pitch-change mechanism
US5174716A (en) * 1990-07-23 1992-12-29 General Electric Company Pitch change mechanism
US5154372A (en) * 1990-07-23 1992-10-13 General Electric Company Torque multiplier for aircraft propeller
US5154580A (en) * 1990-07-23 1992-10-13 General Electric Company Propeller pitch change mechanism
US5152668A (en) * 1990-07-23 1992-10-06 General Electric Company Pitch change mechanism for prop fans
US5242265A (en) * 1990-07-23 1993-09-07 General Electric Company Aircraft pitch change mechanism
US6139272A (en) * 1996-04-29 2000-10-31 Kvaerner Turbin Aktiebolag Hydraulic machine
FR2964942A1 (fr) * 2010-09-22 2012-03-23 Snecma Enceinte de protection des pignons de commande du pas d'une helice d'open-rotor
US9677421B2 (en) 2012-10-24 2017-06-13 United Technologies Corporation Gas turbine engine rotor drain feature
US20160186584A1 (en) * 2013-08-14 2016-06-30 Snecma Turbomachine impellor rotor with device for feathering the blades of the impellor
US10036262B2 (en) * 2013-08-14 2018-07-31 Snecma Turbomachine impellor rotor with device for feathering the blades of the impellor
US10400883B2 (en) 2017-01-04 2019-09-03 United Technologies Corporation Gear with fluid control dam and apertures
US11155334B2 (en) * 2018-03-12 2021-10-26 Ge Avio S.R.L Fan blade support assembly
US11719107B2 (en) * 2018-10-12 2023-08-08 Safran Aircraft Engines Turbine engine comprising a rotor with variable-pitch blades

Also Published As

Publication number Publication date
GB1516349A (en) 1978-07-05
FR2286949B1 (enExample) 1979-09-07
JPS5162259A (en) 1976-05-29
FR2286949A1 (fr) 1976-04-30

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